Development of a Multi-Segment Parallel Compressor Model for a Boundary Layer Ingesting Fuselage Fan Stage

The present methodological study aims to assess boundary layer ingestion (BLI) as a promising method improve propulsion efficiency. BLI utilizes the low momentum inflow of wing or fuselage for thrust generation in order minimize required propulsive power given amount fuselage-embedded engines. A multi-segment parallel compressor model (PCM) is developed calculate saving from full annular occurring at tail center-mounted aircraft engine, employing radially subdivided fan characteristics. Applying this methodology, adverse effects on performance due varying inlet distortions depending flight operating point well upstream suction can be taken into account. This marks one step onto further segmented PCM general cases BLI-induced distortion and allows evaluation synergies between combined active laminar flow control drag reduction measure. study, therefore, presents towards lower fuel consumption and, hence, environmental impact future transport aircraft.